WO2014009089A1 - Protective layer for a component of a turbomachine - Google Patents

Protective layer for a component of a turbomachine Download PDF

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Publication number
WO2014009089A1
WO2014009089A1 PCT/EP2013/062155 EP2013062155W WO2014009089A1 WO 2014009089 A1 WO2014009089 A1 WO 2014009089A1 EP 2013062155 W EP2013062155 W EP 2013062155W WO 2014009089 A1 WO2014009089 A1 WO 2014009089A1
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WO
WIPO (PCT)
Prior art keywords
component
hard material
layer
material layer
ceramic hard
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PCT/EP2013/062155
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German (de)
French (fr)
Inventor
Jochen Barnikel
Manuel Ettler
Friedhelm Schmitz
Jörg SCHÜRHOFF
Original Assignee
Siemens Aktiengesellschaft
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Priority to CN201390000611.5U priority Critical patent/CN204803410U/en
Publication of WO2014009089A1 publication Critical patent/WO2014009089A1/en

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer

Definitions

  • the invention relates to a component for a turbomachine, in particular steam turbine, with a component surface.
  • a component for a turbomachine in particular steam turbine
  • Protective coatings for high operating temperatures are commonly used today in turbomachinery.
  • the main field of application of such high-temperature protective layers is found in the field of thermal turbomachines, especially in highly stressed steam turbine components.
  • Such protective layers serve to extend the service life of the high-temperature materials to be protected.
  • Zones of a steam turbine can be used to fulfill two characteristics. These are on the one hand the oxidation resistance and on the other hand the creep rupture strength. Basically, materials are known that can meet such requirements, such as nickel-based alloys, which are increasingly used. However, such materials are relatively expensive. Therefore, the materials mentioned above are replaced by much cheaper materials, such as ferritic 10% chromium steel or similar replaced. The disadvantage of such ferritic 10% chromium steels or other similar materials is that they do not have sufficient oxidation resistance and are therefore unsuitable for some applications in the steam turbine.
  • the thermally stressed components have been exposed in areas exposed to approximately 600 ° C hot steam, such as e.g. High-pressure or medium-pressure turbine blades, partially made of nickel-based alloys.
  • the established chromium steels are generally no longer used at steam temperatures in the range of well above 600 ° C., since the oxidation resistance of such chromium steels in this range is no longer sufficient.
  • a component for a turbomachine in particular a steam turbine, with a component surface, wherein a ceramic hard material layer is applied directly to the component surface, wherein a metallic layer is applied directly to the ceramic hard material layer.
  • a duplex protective layer consisting of two layers is applied to the component.
  • the component has a component surface, wherein a ceramic hard material layer is arranged directly on this component surface. It is essential here that the ceramic hard material layer is applied directly to the component surface, ie, that no intermediate layer is arranged between the component surface and the ceramic hard material layer.
  • a metallic layer is applied directly to this ceramic hard material layer. It is also important here again that no further intermediate layer is arranged between the ceramic hard material layer and the metallic layer.
  • the invention is based on the idea that the duplex layer according to the invention offers improved oxidation protection and improved erosion resistance. This means that the base material of the component does not necessarily have to be a nickel-based alloy. Instead, cheaper materials can be used instead of the nickel-based alloy.
  • the component has the following materials:
  • High temperature suitable Cr alloyed steels for use in turbomachines such as e.g. X20Cr13 (1.4021),
  • the metallic layer comprises the following materials:
  • the duplex layer is further developed into a triplex layer by applying a second ceramic hard material layer directly to the metallic layer.
  • a second ceramic hard material layer directly to the metallic layer.
  • the ceramic hard material layer is arranged directly on the metallic layer, ie that no further intermediate layer is applied between the ceramic hard material layer and the metallic layer.
  • the second ceramic hard material layer comprises the following materials:
  • the thicknesses of the ceramic hard material layer, the metallic protective layer and the second ceramic hard material layer have thicknesses in the range of 5 ⁇ to 25 ⁇ .
  • FIG. 1 shows a duplex protective layer according to the invention
  • FIG. 2 shows a triplex protective layer according to the invention.
  • FIG. 1 shows a component 1.
  • This component is designed for use in a turbomachine.
  • turbomachine is understood, for example, a steam turbine, a compressor or a gas turbine or other thermal machines.
  • the component has a component surface 2.
  • a ceramic hard material layer 3 is arranged directly.
  • the ceramic hard material layer 3 is arranged directly on the component surface, ie no further layer is arranged between the ceramic hard material layer 3 and the component surface 2.
  • a metallic layer 4 is arranged directly.
  • the metallic one Layer 4 is arranged directly on the ceramic hard material layer 3, ie no further intermediate layer is arranged between the metallic layer 4 and the ceramic hard material layer 3.
  • the component contains the following materials:
  • High temperature suitable Cr alloyed steels for use in turbomachines such as e.g. X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1- (1.4906), 10CrMo9-10 (1.7380).
  • the chemical compositions are as follows (in% by weight):
  • MO 1.00 - 1.20 N: 0, 040 - 0.060
  • Nb 0, 040-0.060
  • the ceramic hard material layer comprises the following materials:
  • the metallic layer comprises the following materials:
  • the embodiment according to FIG. 1 can be referred to as a duplex layer, since the protective layer protects against erosion and
  • Oxidation on the component surface 2 comprises two layers.
  • FIG. 2 shows a further development of the component from FIG. 1.
  • the further development consists in the fact that a second ceramic hard material layer 5 is now applied to the metallic layer 4.
  • the second ceramic hard material layer 3 comprises the following materials: - CrN
  • the ceramic hard material layer 3 is formed such that the thickness of the ceramic hard material layer 3 is in the range of 5 ⁇ to 25 ⁇ .
  • the metallic layer 4 is formed such that the metallic layer 4 has a thickness which is in the range between 5 ⁇ and 25 ⁇ .
  • the second ceramic hard material layer 5 is formed in such a way that the second ceramic hard material layer 5 has a thickness which lies in the range between 5 ⁇ m to 25 ⁇ m.
  • the component is designed, for example, as a turbine blade for a steam turbine.
  • the turbine blade may be a rotor blade or a vane.
  • the combination of the two layers comprising the ceramic hard material layer 3 and the metallic layer 4 form a very good protection of the component 1 against oxidation and at the same time also offer good erosion resistance.
  • the ceramic hard material layer 3 acts primarily as a diffusion barrier, which ensures that interdiffusion between the base material of the component 1 and the metallic protective layer 4 does not occur. In addition, this layer already offers good oxidation protection.
  • the metallic layer 4 offers a very good protection against oxidation and erosion, in particular against particles which strike the surface perpendicular to the surface.
  • the triplex layer is carried out at sites particularly subject to erosion.
  • the second ceramic hard material layer 5 in the triplex layer offers particularly good protection as erosion protection and additionally as oxidation protection.
  • the duplex and / or triplex layers are preferably applied by means of a PVD method, in which case in particular sputtering methods are to be used.

Abstract

The invention relates to a component (1) for a steam turbine, a duplex and/or triplex layer being applied to the component (1), the duplex layer consisting of a ceramic hard material layer (3) and of a metallic layer (4) that are directly applied to the component surface (2), the triplex layer consisting of a ceramic hard material layer (3), of a metallic layer (4) and of a further ceramic hard material layer (5) that are directly applied to the component surface (2).

Description

Beschreibung description
Schutzschicht für eine Komponente einer Strömungsmaschine Protective layer for a component of a turbomachine
Die Erfindung betrifft eine Komponente für eine Strömungsmaschine, insbesondere Dampfturbine, mit einer Komponentenoberfläche . Schutzschichten für hohe Betriebstemperaturen werden heute im Strömungsmaschinenbau allgemein häufig verwendet. Das Hauptanwendungsgebiet derartiger Hochtemperatur-Schutzschichten findet sich im Bereich thermischer Strömungsmaschinen, insbesondere bei hochbeanspruchten Dampfturbinen-Komponenten . Sol- che Schutzschichten dienen zur Verlängerung der Lebensdauer der zu schützenden Hochtemperatur-Werkstoffe. The invention relates to a component for a turbomachine, in particular steam turbine, with a component surface. Protective coatings for high operating temperatures are commonly used today in turbomachinery. The main field of application of such high-temperature protective layers is found in the field of thermal turbomachines, especially in highly stressed steam turbine components. Such protective layers serve to extend the service life of the high-temperature materials to be protected.
Dampfturbinen-Laufschaufeln werden in Umgebungen eingesetzt, in der sie hohen zentrifugalen Belastungen und Schwingungs- beanspruchungen ausgesetzt sind. Steam turbine blades are used in environments exposed to high levels of centrifugal stress and vibration.
Schwingungsbeanspruchungen nehmen zu, wenn die Laufschaufei - Eigenfrequenzen mit Betriebsdrehzahlen oder anderen vorübergehenden Frequenzen in Resonanz kommen. Vibration stresses increase as the blade natural frequencies resonate at operating speeds or other transient frequencies.
Für Komponenten einer Hochdruck- und/oder Mitteldruck-Dampfturbine, wie insbesondere Turbinenschaufeln, die mehr als ca. 600°C heißem Dampf ausgesetzt sind, ergeben sich besondere Anforderungen an die zu verwendenden Werkstoffe. Im Wesentli- chen müssen die Werkstoffe, die in thermisch beanspruchtenFor components of a high-pressure and / or medium-pressure steam turbine, in particular turbine blades, which are exposed to more than about 600 ° C hot steam, there are special requirements for the materials to be used. Essentially, the materials that are in thermal stress
Zonen einer Dampfturbine verwendet werden, zwei Eigenschaften erfüllen. Dies sind zum einen die Oxidationsbeständigkeit und zum anderen die Zeitstandsfestigkeit. Im Grunde genommen sind Werkstoffe bekannt, die solche Anforderungen erfüllen können, wie z.B. Nickel-Basis-Legierungen, die vermehrt zum Einsatz kommen. Allerdings sind solche Werkstoffe vergleichsweise teuer. Daher werden die vorgenannten Werkstoffe durch wesentlich preiswertere Werkstoffe, wie z.B. ferritische 10%-Chrom- stähle oder ähnliche ersetzt. Der Nachteil solcher ferritischen 10%-igen Chromstähle oder anderer ähnlicher Werkstoffe liegt darin, dass diese keine hinreichende Oxidationsbe- ständigkeit besitzen und daher ungeeignet sind für manche Anwendungen in der Dampfturbine. Zones of a steam turbine can be used to fulfill two characteristics. These are on the one hand the oxidation resistance and on the other hand the creep rupture strength. Basically, materials are known that can meet such requirements, such as nickel-based alloys, which are increasingly used. However, such materials are relatively expensive. Therefore, the materials mentioned above are replaced by much cheaper materials, such as ferritic 10% chromium steel or similar replaced. The disadvantage of such ferritic 10% chromium steels or other similar materials is that they do not have sufficient oxidation resistance and are therefore unsuitable for some applications in the steam turbine.
Bisher wurden die thermisch beanspruchten Komponenten in Bereichen, die ca. 600°C heißem Dampf ausgesetzt sind, wie z.B. Hochdruck- bzw. Mitteldruck-Turbinenschaufeln, teilweise aus Nickel-Basis-Legierungen hergestellt. Die etablierten Chromstähle werden in der Regel bei Dampftemperaturen im Bereich von deutlich über 600°C nicht mehr verwendet, da die Oxidati- onsbeständigkeit solcher Chromstähle in diesem Bereich nicht mehr ausreichend ist. Heretofore, the thermally stressed components have been exposed in areas exposed to approximately 600 ° C hot steam, such as e.g. High-pressure or medium-pressure turbine blades, partially made of nickel-based alloys. The established chromium steels are generally no longer used at steam temperatures in the range of well above 600 ° C., since the oxidation resistance of such chromium steels in this range is no longer sufficient.
Es ist Aufgabe der Erfindung, eine geeignete Schutzschicht für eine Komponente einer Strömungsmaschine anzugeben. It is an object of the invention to provide a suitable protective layer for a component of a turbomachine.
Gelöst wird diese Aufgabe durch eine Komponente für eine Strömungsmaschine, insbesondere Dampfturbine, mit einer Komponentenoberfläche, wobei direkt auf die Komponentenoberfläche eine keramische Hartstoffschicht appliziert ist, wobei direkt auf die keramische Hartstoffschicht eine metallische Schicht aufgebracht ist. This object is achieved by a component for a turbomachine, in particular a steam turbine, with a component surface, wherein a ceramic hard material layer is applied directly to the component surface, wherein a metallic layer is applied directly to the ceramic hard material layer.
Ein wesentliches Merkmal ist, dass auf die Komponente eine Duplexschutzschicht aufgebracht wird, die aus zwei Schichten besteht. Die Komponente weist eine Komponentenoberfläche auf, wobei direkt auf diese Komponentenoberfläche eine keramische Hartstoffschicht angeordnet ist. Wesentlich hierbei ist, dass die keramische Hartstoffschicht direkt auf die Komponentenoberfläche aufgebracht wird, d.h., dass zwischen der Komponentenoberfläche und der keramischen Hartstoffschicht keine Zwischenschicht angeordnet ist. Erfindungsgemäß wird auf diese keramische Hartstoffschicht direkt eine metallische Schicht aufgebracht. Wesentlich ist hierbei auch wiederum, dass zwischen der keramischen Hartstoffschicht und der metallischen Schicht keine weitere Zwischenschicht angeordnet ist. Die Erfindung geht von dem Gedanken aus, dass die erfindungs- gemäße Duplexschicht einen verbesserten Oxidationsschutz und eine verbesserte Erosionsbeständigkeit bietet. Das bedeutet, dass der Grundwerkstoff der Komponente nicht zwingend eine Nickel-Basis-Legierung sein muss. Es können vielmehr preiswertere Werkstoffe statt der Nickel-Basis-Legierung verwendet werden . Vorteilhafte Weiterbildungen sind in den Unteransprüchen angegeben . An essential feature is that a duplex protective layer consisting of two layers is applied to the component. The component has a component surface, wherein a ceramic hard material layer is arranged directly on this component surface. It is essential here that the ceramic hard material layer is applied directly to the component surface, ie, that no intermediate layer is arranged between the component surface and the ceramic hard material layer. According to the invention, a metallic layer is applied directly to this ceramic hard material layer. It is also important here again that no further intermediate layer is arranged between the ceramic hard material layer and the metallic layer. The invention is based on the idea that the duplex layer according to the invention offers improved oxidation protection and improved erosion resistance. This means that the base material of the component does not necessarily have to be a nickel-based alloy. Instead, cheaper materials can be used instead of the nickel-based alloy. Advantageous developments are specified in the subclaims.
In einer ersten vorteilhaften Weiterbildung weist die Komponente folgende Materialien auf: In a first advantageous development, the component has the following materials:
- Hochtemperaturgeeignete Cr- legierte Stähle für die Anwendung in Strömungsmaschinen, wie z.B. X20Crl3 (1.4021), High temperature suitable Cr alloyed steels for use in turbomachines, such as e.g. X20Cr13 (1.4021),
X22CrMoV12-l (1.4923), X12CrMoWVNbN10 - 1 - 1 (1.4906), 10CrMo9- 10 (1.7380) . X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1- (1.4906), 10CrMo9-10 (1.7380).
Die keramische HartstoffSchicht weist vorteilhafterweise folgende Materialien auf: The ceramic hard material layer advantageously has the following materials:
- CrN - CrN
- CrAlN - CrAIN
- TiAlN  - TiAlN
- A1203 - A1 2 0 3
In einer weiteren vorteilhaften Weiterbildung weist die metallische Schicht folgende Materialien auf: In a further advantageous development, the metallic layer comprises the following materials:
- metallische Schicht des Typs MCrAl (Y) oder Ni-basierte Schichten mit mindestens 15% Cr. In einer wesentlichen vorteilhaften Weiterbildung wird die Duplexschicht zu einer Triplexschicht weitergebildet, indem direkt auf der metallischen Schicht eine zweite keramische Hartstoffschicht aufgebracht ist. Das bedeutet, dass die Korn- ponente nunmehr drei Schichten übereinander aufweist. Wesentliches Merkmal hierbei ist, dass die keramische Hartstoff- Schicht direkt auf der metallischen Schicht angeordnet ist, d.h. dass zwischen der keramischen HartstoffSchicht und der metallischen Schicht keine weitere Zwischenschicht aufgebracht ist. In einer vorteilhaften Weiterbildung umfasst die zweite keramische HartstoffSchicht folgende Materialien: Metallic layer of the MCrAl (Y) type or Ni-based layers of at least 15% Cr. In a significant advantageous development, the duplex layer is further developed into a triplex layer by applying a second ceramic hard material layer directly to the metallic layer. This means that the grain component now has three layers one above the other. An essential feature here is that the ceramic hard material layer is arranged directly on the metallic layer, ie that no further intermediate layer is applied between the ceramic hard material layer and the metallic layer. In an advantageous development, the second ceramic hard material layer comprises the following materials:
- CrN  - CrN
- CrAlN  - CrAIN
- TiAlN - TiAlN
- A1203 - A1 2 0 3
In vorteilhaften Weiterbildungen weisen die Dicken der keramischen HartstoffSchicht , der metallischen Schutzschicht und der zweiten keramischen HartstoffSchicht Dicken im Bereich von 5μπι bis 25μπι auf. In advantageous developments, the thicknesses of the ceramic hard material layer, the metallic protective layer and the second ceramic hard material layer have thicknesses in the range of 5μπι to 25μπι.
Die Erfindung wird anhand eines Ausführungsbeispiels nun näher erläutert . The invention will now be explained in more detail with reference to an embodiment.
Es zeigen: Show it:
Figur 1 eine erfindungsgemäße Duplex-Schutzschicht ; FIG. 1 shows a duplex protective layer according to the invention;
Figur 2 eine erfindungsgemäße Triplex-Schutzschicht . FIG. 2 shows a triplex protective layer according to the invention.
Figur 1 zeigt eine Komponente 1. Diese Komponente ist ausgebildet zur Verwendung in einer Strömungsmaschine. Unter Strömungsmaschine wird bspw. eine Dampfturbine, ein Verdichter oder eine Gasturbine oder weitere thermische Maschinen verstanden. Die Komponente weist eine Komponentenoberfläche 2 auf. Auf diese Komponentenoberfläche 2 wird direkt eine keramische Hartstoffschicht 3 angeordnet. Die keramische Hartstoffschicht 3 wird direkt auf die Komponentenoberfläche an- geordnet, d.h. zwischen der keramischen Hartstoffschicht 3 und der Komponentenoberfläche 2 ist keine weitere Schicht angeordnet. Auf die keramische Hartstoffschicht wird direkt eine metallische Schicht 4 angeordnet. Die metallische Schicht 4 wird direkt auf der keramischen HartstoffSchicht 3 angeordnet, d.h. zwischen der metallischen Schicht 4 und der keramischen HartstoffSchicht 3 ist keine weitere Zwischenschicht angeordnet . FIG. 1 shows a component 1. This component is designed for use in a turbomachine. By turbomachine is understood, for example, a steam turbine, a compressor or a gas turbine or other thermal machines. The component has a component surface 2. On this component surface 2, a ceramic hard material layer 3 is arranged directly. The ceramic hard material layer 3 is arranged directly on the component surface, ie no further layer is arranged between the ceramic hard material layer 3 and the component surface 2. On the ceramic hard material layer, a metallic layer 4 is arranged directly. The metallic one Layer 4 is arranged directly on the ceramic hard material layer 3, ie no further intermediate layer is arranged between the metallic layer 4 and the ceramic hard material layer 3.
Die Komponente weist folgende Materialien auf: The component contains the following materials:
- Hochtemperaturgeeignete Cr- legierte Stähle für die Anwendung in Strömungsmaschinen, wie z.B. X20Crl3 (1.4021), X22CrMoV12-l (1.4923), X12CrMoWVNbN10 - 1 - 1 (1.4906), 10CrMo9- 10 (1.7380) . High temperature suitable Cr alloyed steels for use in turbomachines, such as e.g. X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1- (1.4906), 10CrMo9-10 (1.7380).
Die chemischen Zusammensetzungen sind folgendermaßen (in Gew. -%) : The chemical compositions are as follows (in% by weight):
X20Crl3 (1.4021) : C: 0,16 - 0,25  X20Cr13 (1.4021): C: 0.16-0.25
Si : <= 1,00  Si: <= 1.00
Mn: <= 1,50  Mn: <= 1.50
P: <= 0,04  P: <= 0.04
S : <= 0,015  S: <= 0.015
Cr: 12,00 - 14,00  Cr: 12.00 - 14.00
X22CrMoV12-l (1.4923: C: 0,18 - 0, 24 X22 CrMoV12-I (1.4923: C: 0.18-0.24
Si : <= 0,50  Si: <= 0.50
Mn: <= 0,40 - 0,90  Mn: <= 0.40-0.90
P: <= 0,025  P: <= 0.025
S : <= 0,015  S: <= 0.015
Cr: 11,00 - 12,50  Cr: 11.00 - 12.50
MO: 0,80 - 1,20  MO: 0.80 - 1.20
Ni : 0,30 - 0,80  Ni: 0.30 - 0.80
V: 0,25 - ,035  V: 0.25 -, 035
X12CrMoWVNbN10-l-l (1.4906] C: 0,10 - 0, 14 X12CrMoWVNbN10-l-1 (1.4906) C: 0.10-0.14
Si : <= 0,10  Si: <= 0.10
Mn: 0,40 - 0,60  Mn: 0.40-0.60
P: <= 0,015  P: <= 0.015
S : <= 0,007  S: <= 0.007
AI : <= 0,0120  AI: <= 0.0120
Cr: 10,00 - 11,00  Cr: 10.00 - 11.00
MO: 1,00 - 1,20 N: 0, 040 - 0,060 MO: 1.00 - 1.20 N: 0, 040 - 0.060
Nb: 0, 040 - 0,060  Nb: 0, 040-0.060
Ni : 0,60 - 0,80  Ni: 0.60 - 0.80
V: 0,15 - 0,25  V: 0.15-0.25
W: 0,95 - 1,10  W: 0.95 - 1.10
10CrMo9-10 (1.7380) : C: 0,08 - 0, 14 10CrMo9-10 (1.7380): C: 0.08-0.14
Si : <= 0,50  Si: <= 0.50
Mn: 0,30 - 0,70  Mn: 0.30-0.70
P: <= 0,025  P: <= 0.025
S : <= 0,020  S: <= 0.020
AI : <= 0,0400  AI: <= 0.0400
Cr: 2, 00 - 2, 50  Cr: 2, 00 - 2, 50
Cu: <= 0,30  Cu: <= 0.30
MO: 0,90 - 1,10  MO: 0,90 - 1,10
Ni : <= 0,30  Ni: <= 0.30
Die keramische HartstoffSchicht weist folgende Materialien auf : The ceramic hard material layer comprises the following materials:
- CrN - CrN
- CrAlN  - CrAIN
- TiAlN  - TiAlN
- A1203 Die metallische Schicht weist folgende Materialien auf: - A1 2 0 3 The metallic layer comprises the following materials:
- metallische Schicht des Typs MCrAl (Y) oder Ni-basierte Schichten mit mindestens 15% Cr.  Metallic layer of the MCrAl (Y) type or Ni-based layers of at least 15% Cr.
Die Ausführungsform gemäß Figur 1 kann als eine Duplexschicht bezeichnet werden, da die Schutzschicht gegen Erosion undThe embodiment according to FIG. 1 can be referred to as a duplex layer, since the protective layer protects against erosion and
Oxidation auf der Komponentenoberfläche 2 zwei Schichten um- fasst . Oxidation on the component surface 2 comprises two layers.
Die Figur 2 zeigt eine Weiterbildung der Komponente aus Figur 1. Die Weiterbildung besteht darin, dass nunmehr auf die metallische Schicht 4 eine zweite keramische HartstoffSchicht 5 aufgebracht ist. Die zweite keramische HartstoffSchicht 3 weist folgende Materialien auf: - CrN FIG. 2 shows a further development of the component from FIG. 1. The further development consists in the fact that a second ceramic hard material layer 5 is now applied to the metallic layer 4. The second ceramic hard material layer 3 comprises the following materials: - CrN
- CrAlN  - CrAIN
- TiAlN  - TiAlN
- A1203 - A1 2 0 3
Die keramische HartstoffSchicht 3 wird derart ausgebildet, dass die Dicke der keramischen HartstoffSchicht 3 im Bereich von 5μπι bis 25μπι liegt. Die metallische Schicht 4 wird derart ausgebildet, dass die metallische Schicht 4 eine Dicke aufweist, die im Bereich zwischen 5μπι und 25μπι liegt. The ceramic hard material layer 3 is formed such that the thickness of the ceramic hard material layer 3 is in the range of 5μπι to 25μπι. The metallic layer 4 is formed such that the metallic layer 4 has a thickness which is in the range between 5μπι and 25μπι.
Die zweite keramische HartstoffSchicht 5 wird derart ausge- bildet, dass die zweite keramische HartstoffSchicht 5 eine Dicke aufweist, die im Bereich zwischen 5μπι bis 25μπι liegt. The second ceramic hard material layer 5 is formed in such a way that the second ceramic hard material layer 5 has a thickness which lies in the range between 5 μm to 25 μm.
Die Komponente wird beispielsweise als Turbinenschaufel für eine Dampfturbine ausgebildet. Die Turbinenschaufel kann eine Laufschaufei oder eine Leitschaufel sein. Die Kombination der beiden Schichten umfassend die keramische HartstoffSchicht 3 und die metallische Schicht 4 bilden einen sehr guten Schutz der Komponente 1 gegen Oxidation und bieten auch gleichzeitig eine gute Erosionsbeständigkeit. The component is designed, for example, as a turbine blade for a steam turbine. The turbine blade may be a rotor blade or a vane. The combination of the two layers comprising the ceramic hard material layer 3 and the metallic layer 4 form a very good protection of the component 1 against oxidation and at the same time also offer good erosion resistance.
Die keramische HartstoffSchicht 3 fungiert dabei in erster Linie als Diffusionsbarriere, die sicherstellt, dass es nicht zur Interdiffusion zwischen Grundwerkstoff der Komponente 1 und der metallischen Schutzschicht 4 kommt. Zusätzlich bietet diese Schicht bereits einen guten Oxidationsschutz . Die metallische Schicht 4 bietet einen sehr guten Oxidations- und Erosionsschutz, insbesondere gegenüber senkrecht auf die Oberfläche treffende Partikel . Die Triplexschicht wird an besonders durch Erosion belasteten Stellen ausgeführt. Die zweite keramische HartstoffSchicht 5 in der Triplexschicht bietet einen besonders guten Schutz als Erosionsschutz und zusätzlich als Oxidationsschutz. Die Duplex- und/oder Triplexschichten werden bevorzugt mittels eines PVD-Verfahrens , wobei hier insbesondere Sputter- Verfahren verwendet werden sollen, aufgebracht. The ceramic hard material layer 3 acts primarily as a diffusion barrier, which ensures that interdiffusion between the base material of the component 1 and the metallic protective layer 4 does not occur. In addition, this layer already offers good oxidation protection. The metallic layer 4 offers a very good protection against oxidation and erosion, in particular against particles which strike the surface perpendicular to the surface. The triplex layer is carried out at sites particularly subject to erosion. The second ceramic hard material layer 5 in the triplex layer offers particularly good protection as erosion protection and additionally as oxidation protection. The duplex and / or triplex layers are preferably applied by means of a PVD method, in which case in particular sputtering methods are to be used.

Claims

Patentansprüche claims
1. Komponente (1) für eine Strömungsmaschine, insbesondere Dampfturbine, mit einer Komponentenoberfläche (2), 1. component (1) for a turbomachine, in particular steam turbine, with a component surface (2),
wobei direkt auf die Komponentenoberfläche (2) eine keramische HartstoffSchicht (3) appliziert ist,  wherein a ceramic hard material layer (3) is applied directly to the component surface (2),
wobei direkt auf die keramische HartstoffSchicht (3) eine metallische Schicht (4) aufgebracht ist.  wherein a metallic layer (4) is applied directly to the ceramic hard material layer (3).
2. Komponente (1) nach Anspruch 1, 2. Component (1) according to claim 1,
wobei die Komponente folgende Materialien aufweist:  wherein the component comprises the following materials:
- hochtemperaturgeeignete Cr- legierte Stähle für die Anwendung in Strömungsmaschinen, wie z.B. X20Crl3 (1.4021), X22CrMoV12-l (1.4923), X12CrMoWVNbN10 - 1 - 1 (1.4906),  high temperature suitable Cr alloyed steels for use in turbomachines, such as e.g. X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1- (1.4906),
10CrMo9-10 (1.7380) .  10CrMo9-10 (1.7380).
3. Komponente (1) nach Anspruch 1 oder 2, 3. component (1) according to claim 1 or 2,
wobei die keramische HartstoffSchicht (3) folgende Materia- lien aufweist:  wherein the ceramic hard material layer (3) has the following materials:
- CrN  - CrN
- CrAlN  - CrAIN
- TiAlN  - TiAlN
- A1203. - A1 2 0 3 .
4. Komponente (1) nach Anspruch 1, 2 oder 3, 4. component (1) according to claim 1, 2 or 3,
wobei die metallische Schicht (4) folgende Materialien aufweist :  wherein the metallic layer (4) comprises the following materials:
- metallische Schicht des Typs MCrAl (Y) oder Ni-basierte Schichten mit mindestens 15% Cr.  Metallic layer of the MCrAl (Y) type or Ni-based layers of at least 15% Cr.
5. Komponente (1) nach einem der Ansprüche 1 bis 4, 5. Component (1) according to one of claims 1 to 4,
wobei direkt auf der metallischen Schicht (4) eine zweite keramische HartstoffSchicht (5) aufgebracht ist. wherein directly on the metallic layer (4) a second ceramic hard material layer (5) is applied.
6. Komponente (1) nach einem der Ansprüche 1 bis 5, 6. Component (1) according to one of claims 1 to 5,
wobei die zweite keramische HartstoffSchicht (5) folgende Materialien aufweist:  wherein the second ceramic hard material layer (5) comprises the following materials:
- CrN  - CrN
- CrAlN  - CrAIN
- TiAlN  - TiAlN
- A1203. - A1 2 0 3 .
7. Komponente (1) nach einem der Ansprüche 1 bis 6, 7. component (1) according to one of claims 1 to 6,
wobei die keramische HartstoffSchicht (3) eine Dicke im Bereich von 5μπι bis 25μπι aufweist.  wherein the ceramic hard material layer (3) has a thickness in the range of 5μπι to 25μπι.
8. Komponente (1) nach einem der Ansprüche 1 bis 7, 8. Component (1) according to one of claims 1 to 7,
wobei die metallische Schicht (4) eine Dicke im Bereich von 5μπι bis 25μπι aufweist.  wherein the metallic layer (4) has a thickness in the range of 5μπι to 25μπι.
9. Komponente (1) nach einem der Ansprüche 1 bis 8, 9. component (1) according to one of claims 1 to 8,
wobei die zweite keramische HartstoffSchicht (5) eine Dicke im Bereich von 5μπι bis 25μπι aufweist.  wherein the second ceramic hard material layer (5) has a thickness in the range of 5μπι to 25μπι.
10. Komponente (1) nach einem der vorhergehenden Ansprüche, ausgeführt als Schaufel für eine Strömungsmaschine. 10. Component (1) according to one of the preceding claims, designed as a blade for a turbomachine.
PCT/EP2013/062155 2012-07-11 2013-06-12 Protective layer for a component of a turbomachine WO2014009089A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201390000611.5U CN204803410U (en) 2012-07-11 2013-06-12 A part for fluid machinery

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP12175910.4 2012-07-11
EP12175910.4A EP2684982A1 (en) 2012-07-11 2012-07-11 Protective coating for a component of a fluid flow engine

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Publication number Priority date Publication date Assignee Title
EP2907888A1 (en) 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Compressor blade with erosion resistant hard material coating
DE102016222296A1 (en) 2016-11-14 2018-05-17 Siemens Aktiengesellschaft Multi-layer aluminum-containing protective coating and component

Citations (5)

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Publication number Priority date Publication date Assignee Title
AT7941U1 (en) * 2004-12-02 2005-11-15 Ceratizit Austria Gmbh TOOL FOR DISCONTINUING MACHINING
US20070078521A1 (en) * 2005-09-30 2007-04-05 Depuy Products, Inc. Aluminum oxide coated implants and components
DE102007050918A1 (en) * 2006-10-26 2008-04-30 General Electric Co. Turbine components have erosion-resistant coating applied using electron beam physical vapor deposition or ion plasma arc coating
DE102007027335A1 (en) * 2007-06-14 2008-12-18 Mtu Aero Engines Gmbh Wear protection coating and component with a wear protection coating
EP2072636A2 (en) * 2007-12-21 2009-06-24 Sandvik Intellectual Property AB Method of making a coated cutting tool, and cutting tools thereof

Patent Citations (5)

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Publication number Priority date Publication date Assignee Title
AT7941U1 (en) * 2004-12-02 2005-11-15 Ceratizit Austria Gmbh TOOL FOR DISCONTINUING MACHINING
US20070078521A1 (en) * 2005-09-30 2007-04-05 Depuy Products, Inc. Aluminum oxide coated implants and components
DE102007050918A1 (en) * 2006-10-26 2008-04-30 General Electric Co. Turbine components have erosion-resistant coating applied using electron beam physical vapor deposition or ion plasma arc coating
DE102007027335A1 (en) * 2007-06-14 2008-12-18 Mtu Aero Engines Gmbh Wear protection coating and component with a wear protection coating
EP2072636A2 (en) * 2007-12-21 2009-06-24 Sandvik Intellectual Property AB Method of making a coated cutting tool, and cutting tools thereof

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